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Microwave Oven With Removable Storage Cassette in Dashboard of Motor Vehicle
A microwave oven adapted for use within a motor vehicle dashboard area. The microwave oven has a removable storage cassette, and slidable platforms for securing and serving containers of beverages and foods.
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| Number | Title | Issue Date |
| 4176814 | Terminally corrected projectile An apparatus for correcting the terminal portion of the ballistic trajectory of a projectile. The projectile is initially fired at a target in a manner to cause the projectile to rotate in flight. At least one detector is mounted on a front surface of the... | 12/04/1979 |
| 4127243 | Device for a missile or the like In a missile assembly (or the like) including a motor nozzle positioned in a central portion of a rear surface of the missile and a sustainer motor positioned a distance away from the rear surface of the missile, the invention comprising a blow pipe joini... | 11/28/1978 |
| 4114451 | Moving coil miniature angular rate sensor A steering rate sensing device for rolling air frames includes a base member for attachment to the air frame, a magnetic member fixed to the base member, and a pick up coil pivotally mounted to the base in close proximity to the magnet such that movement ... | 09/19/1978 |
| 4113204 | Auxiliary control of vehicle direction An auxiliary aerodynamic or hydrodynamic control assembly is provided for a vehicle, such as a guided missile, travelling in a fluid medium, which assembly comprises a number of, say three, control surfaces each carried at the inner end of an arm that is ... | 09/12/1978 |
| 4085909 | Combined warm gas fin and reaction control servo A combined reaction nozzle and fin control servo system to provide separate reaction and fin control of a missile for both high and low velocity flight phases. The servo system automatically provides a high gas flow rate for reaction nozzle control and a ... | 04/25/1978 |
| 4080655 | Device for the transformation of steering control signals from one coordinate system to another A system for the transformation of steering control signals from a plane cartesian coordinate system to a polar coordinate system is disclosed. The system is designed to be self-contained on board a missile. The system is synchronized with roll position, ... | 03/21/1978 |
| 4071211 | Momentum biased active three-axis satellite attitude control system Control of an active three-axis multiple-wheel attitude control system is provided with a bias momentum to achieve stiffness about the pitch axis. With this stiffness, the system overcomes the inherent inability of a zero momentum system employing the sun... | 01/31/1978 |
| 4054254 | Rolling airframe autopilot The autopilot incorporates a single linear accelerometer transducer and a single pitch rate sensor. The outputs of the accelerometer and pitch rate sensor are summed with the command signal in the control circuit. A servo is controlled by the modified con... | 10/18/1977 |
| 4052024 | Pneumatic gear motor application A pneumatic gear motor application in which a tank filled to a predetermined pressure with an inert gas such as nitrogen is heated by a heat squib device to raise the temperature of the gas and also to increase the pressure of the gas in the storage tank ... | 10/04/1977 |
| 4037806 | Control system for rolling missile with target seeker head This invention relates to a servocontrol system for a weapon such as a missile which is a shoulder-launched, infrared-homing, guided missile which provides frontline troops with effective air defense against low altitude enemy aircraft. The weapon, descri... | 07/26/1977 |
| 4034937 | Position reference devices The invention provides an angular position reference device for measuring changes in the attitude of a moving body and comprising a closed chamber filled with a liquid and rotatable about an axis by drive means, and position sensing means such as a vane a... | 07/12/1977 |
| 4033525 | Feedback PDM encoder and method for actuating a pneumatic actuator with a digital autopilot A feedback PDM encoder and method is presented which permits utilization of neumatic pulse duration modulation (PDM) actuators with potentiometer position pickoffs in a digital autopilot loop. The actuator is directly driven by a signal derived in the digi... | 07/05/1977 |
| 4029270 | Mechanical roll rate stabilizer for a rolling missile A stabilizer system for use with an aerodynamic body having pivotal control surfaces to control the roll rate of the body. A pair of high mass members are diametrically supported for radial displacements induced by the centrifugal forces on the body. A pa... | 06/14/1977 |
| 4013245 | Homing projectile An optical guidance system for a spin-stabilized autorotative projectile ing a target radiation detector, a detector cooling means, a fixed-coil electromagnet and a tuned-frequency steering vane. During projectile flight the detector temperature is reduc... | 03/22/1977 |
| 4012018 | All sky pointing attitude control system In a strapped-down gyroscope space vehicle attitude control system, a method and apparatus are provided for gyro drift and input axis misalignment error compensation employing a sun and a star tracker and preselected vehicle calibration maneuvers. During ... | 03/15/1977 |
| 3999729 | Backup wheel for a three axis reaction wheel spacecraft Three-axis attitude control of a substantially zero momentum satellite is achieved by a control system which includes three mutually orthogonal reaction wheels and a fourth backup reaction wheel. The backup wheel is mounted on an axis which is skewed with... | 12/28/1976 |
| 3998409 | Minimization of spacecraft attitude error due to wheel speed reversal An attitude control system for a substantially zero momentum spacecraft is arranged to minimize the attitude errors during periods of reaction wheel speed reversals. Wheel speed is sensed by a suitable device such as a tachometer or Hall elements. Spacecr... | 12/21/1976 |
| 3990659 | Low cost attitude position sensor for high speed vehicles A pair of electrostatic sensors are recessed in the outer wall of a superic ballistic body. The vertical electrostatic gradient in the atmosphere produces a voltage differential between the sensors when one sensor is higher than the other. Since the fixe... | 11/09/1976 |
| 3990657 | Method and apparatus for reducing ballistic missile range errors due to viscosity uncertainties (U) Errors in the trajectories of balistic missiles result from a number of ces such as the velocity uncertainty of the missile during its powered flight. Prediction of these errors provides the missile circular error probability (CEP) usually in the form of... | 11/09/1976 |
| 3986683 | Jet tab steerable missile A jet tab steerable missile having a plurality of tab-shaped elements rotatably mounted on the rear portion of the missile adjacent the nozzle. The tab-shaped elements are capable of 360° rotary movement from a thrust vector control position into the air... | 10/19/1976 |
| 3984072 | Attitude control system An attitude control system for a space vehicle in which angular rate signals are generated by rate gyros mounted closely adjacent to gimbaled engines at the rear of a vehicle, and wherein error signals representative of a commanded change in vehicle angle... | 10/05/1976 |
| 3979089 | Vertical sensing and control system A rocket powered escape vehicle is equipped with an electrostatic attitude ensing system which commands a rocket motor mounted in gimbals on the bottom of the vehicle to provide a vertically upward seeking escape from an aircraft independent of aircraft at... | 09/07/1976 |
| 3976266 | Missile with cruciform guidance system A missile provided with a cruciform guidance system comprising a pair of north-south and a pair of east-west fins, each pair being coupled with a respective annular support pivotally mounted externally of the body of the missile. A pair of diammetrically ... | 08/24/1976 |
| 3964694 | Aerial acoustic target seeker An acoustic destructive aerial target seeker having recognition-guidance cuitry which is adapted to detect and recognize the characteristic sound emitted from an armored vehicle and to launch and direct the system toward destructive impact with the targe... | 06/22/1976 |
| 3946968 | Apparatus and method for aerodynamic cross-coupling reduction An improved flight control system for use in guided missiles having a plurality of individually actuable control surfaces is shown. In order to overcome the deleterious effects of aerodynamic cross-coupling between control surfaces at a high angle of atta... | 03/30/1976 |
